EP1577499B1 - Turbine components with thermal barrier coatings - Google Patents

Turbine components with thermal barrier coatings Download PDF

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Publication number
EP1577499B1
EP1577499B1 EP05251604A EP05251604A EP1577499B1 EP 1577499 B1 EP1577499 B1 EP 1577499B1 EP 05251604 A EP05251604 A EP 05251604A EP 05251604 A EP05251604 A EP 05251604A EP 1577499 B1 EP1577499 B1 EP 1577499B1
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EP
European Patent Office
Prior art keywords
turbine component
component according
bond coat
coat layer
ceramic material
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Active
Application number
EP05251604A
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German (de)
French (fr)
Other versions
EP1577499A3 (en
EP1577499A2 (en
Inventor
David A. Litton
Nicholas E. Ulion
Mladen F. Trubelja
Michael J. Maloney
Sunil Govinda Warrier
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RTX Corp
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United Technologies Corp
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Publication of EP1577499A3 publication Critical patent/EP1577499A3/en
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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/28—Selecting particular materials; Particular measures relating thereto; Measures against erosion or corrosion
    • F01D5/288—Protective coatings for blades
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B23—MACHINE TOOLS; METAL-WORKING NOT OTHERWISE PROVIDED FOR
    • B23Q—DETAILS, COMPONENTS, OR ACCESSORIES FOR MACHINE TOOLS, e.g. ARRANGEMENTS FOR COPYING OR CONTROLLING; MACHINE TOOLS IN GENERAL CHARACTERISED BY THE CONSTRUCTION OF PARTICULAR DETAILS OR COMPONENTS; COMBINATIONS OR ASSOCIATIONS OF METAL-WORKING MACHINES, NOT DIRECTED TO A PARTICULAR RESULT
    • B23Q11/00—Accessories fitted to machine tools for keeping tools or parts of the machine in good working condition or for cooling work; Safety devices specially combined with or arranged in, or specially adapted for use in connection with, machine tools
    • B23Q11/0042—Devices for removing chips
    • B23Q11/0046—Devices for removing chips by sucking
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B08—CLEANING
    • B08B—CLEANING IN GENERAL; PREVENTION OF FOULING IN GENERAL
    • B08B5/00—Cleaning by methods involving the use of air flow or gas flow
    • B08B5/04—Cleaning by suction, with or without auxiliary action
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    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/01—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics
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    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/01—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics
    • C04B35/48—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on oxide ceramics based on zirconium or hafnium oxides, zirconates, zircon or hafnates
    • C04B35/486—Fine ceramics
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    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/50—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on rare-earth compounds
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    • C04B35/00—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products
    • C04B35/50—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on rare-earth compounds
    • C04B35/505—Shaped ceramic products characterised by their composition; Ceramics compositions; Processing powders of inorganic compounds preparatory to the manufacturing of ceramic products based on rare-earth compounds based on yttrium oxide
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    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/009—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone characterised by the material treated
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    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/45—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements
    • C04B41/50—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials
    • C04B41/5025—Coating or impregnating, e.g. injection in masonry, partial coating of green or fired ceramics, organic coating compositions for adhering together two concrete elements with inorganic materials with ceramic materials
    • C04B41/5042—Zirconium oxides or zirconates; Hafnium oxides or hafnates
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    • C04B41/00—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone
    • C04B41/80—After-treatment of mortars, concrete, artificial stone or ceramics; Treatment of natural stone of only ceramics
    • C04B41/81—Coating or impregnation
    • C04B41/85—Coating or impregnation with inorganic materials
    • C04B41/87—Ceramics
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C14/00—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material
    • C23C14/06—Coating by vacuum evaporation, by sputtering or by ion implantation of the coating forming material characterised by the coating material
    • C23C14/08—Oxides
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C30/00—Coating with metallic material characterised only by the composition of the metallic material, i.e. not characterised by the coating process
    • C—CHEMISTRY; METALLURGY
    • C23—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; CHEMICAL SURFACE TREATMENT; DIFFUSION TREATMENT OF METALLIC MATERIAL; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL; INHIBITING CORROSION OF METALLIC MATERIAL OR INCRUSTATION IN GENERAL
    • C23C—COATING METALLIC MATERIAL; COATING MATERIAL WITH METALLIC MATERIAL; SURFACE TREATMENT OF METALLIC MATERIAL BY DIFFUSION INTO THE SURFACE, BY CHEMICAL CONVERSION OR SUBSTITUTION; COATING BY VACUUM EVAPORATION, BY SPUTTERING, BY ION IMPLANTATION OR BY CHEMICAL VAPOUR DEPOSITION, IN GENERAL
    • C23C4/00—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge
    • C23C4/04—Coating by spraying the coating material in the molten state, e.g. by flame, plasma or electric discharge characterised by the coating material
    • C23C4/10—Oxides, borides, carbides, nitrides or silicides; Mixtures thereof
    • C23C4/11—Oxides
    • C—CHEMISTRY; METALLURGY
    • C04—CEMENTS; CONCRETE; ARTIFICIAL STONE; CERAMICS; REFRACTORIES
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    • C04B2235/00—Aspects relating to ceramic starting mixtures or sintered ceramic products
    • C04B2235/02—Composition of constituents of the starting material or of secondary phases of the final product
    • C04B2235/30—Constituents and secondary phases not being of a fibrous nature
    • C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
    • C04B2235/3224—Rare earth oxide or oxide forming salts thereof, e.g. scandium oxide
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    • C04B2235/3225—Yttrium oxide or oxide-forming salts thereof
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    • C04B2235/3227—Lanthanum oxide or oxide-forming salts thereof
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    • C04B2235/3224—Rare earth oxide or oxide forming salts thereof, e.g. scandium oxide
    • C04B2235/3229—Cerium oxides or oxide-forming salts thereof
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    • C04B2235/32—Metal oxides, mixed metal oxides, or oxide-forming salts thereof, e.g. carbonates, nitrates, (oxy)hydroxides, chlorides
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    • C04B2235/3244—Zirconium oxides, zirconates, hafnium oxides, hafnates, or oxide-forming salts thereof
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    • C04B2235/3286—Gallium oxides, gallates, indium oxides, indates, thallium oxides, thallates or oxide forming salts thereof, e.g. zinc gallate
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
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    • F05D2300/00—Materials; Properties thereof
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    • F05D2300/607—Monocrystallinity
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2300/00—Materials; Properties thereof
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    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to turbine components having a substrate formed from a ceramic material, such as a monolithic ceramic or a composite ceramic material, and a thermal barrier coating made from ceramic materials.
  • Gas turbine engines are well developed mechanisms for converting chemical potential energy, in the form of fuel, to thermal energy and then to mechanical energy for use in propelling aircraft, generating electrical power, pumping fluids, etc.
  • the major available avenue for improved efficiency of gas turbine engines appears to be the use of higher operating temperatures.
  • the metallic materials used in gas turbine engines are currently very near the upper limits of their thermal stability. In the hottest portion of modern gas turbine engines, metallic materials are used at gas temperatures above their melting points. They survive because they are air cooled. But providing air cooling reduces engine efficiency.
  • thermal barrier coatings for use with cooled gas turbine aircraft hardware.
  • the amount of cooling air required can be substantially reduced, thus providing a corresponding increase in efficiency.
  • Such coatings are invariably based on ceramic.
  • Mullite and alumina have been proposed, but zirconia is the current material of choice.
  • Zirconia must be modified with a stabilizer to prevent the formation of the monoclinic phase.
  • Typical stabilizers include yttria, calcia, ceria, and magnesia.
  • Zirconia based ceramics are resistant to water attack.
  • thermal barrier coating can become a problem - indeed it is known to be a problem for silica-based thermal barrier coatings and alumina-based thermal barrier coatings. Steam is often injected into the combustor of land-based gas turbines to reduce nitric oxide formation, which exacerbates the water attack issue.
  • Hafnia and zirconate based materials for thermal/environmental barrier coating applications are disclosed in D. Zhu et al., NASA/TM-2003-212544.
  • thermal barrier coatings which exhibit superior thermal insulation capabilities, especially those improved in insulation capabilities when normalized for coating density.
  • Weight is always a critical factor when designing gas turbine engines, particularly rotating parts.
  • Ceramic thermal barrier coatings are not load supporting materials, and consequently they add weight without increasing strength.
  • a turbine component having a substrate formed from a ceramic material selected from the group consisting of a monolithic ceramic material and a composite ceramic material and a thermal barrier coating bonded to said substrate, said thermal barrier coating consisting of at least 15 mol% of at least one lanthanide sesquioxide and the balance consisting of ceria.
  • the ceria is preferably present in an amount greater than 50 mol%.
  • the at least one lanthanide sesquioxide preferably has a formula A 2 O 3 where A is selected from the group consisting of La, Pr, Nd, Sm, Eu, Tb, and mixtures thereof.
  • the essence of the present invention arises from the discovery that certain ceramic materials have great utility as thermal barrier coatings on ceramic material substrates, particularly those used to form components, such as the airfoils, of turbine engine components. These ceramic coating materials have such utility because they exhibit lower thermal conductivity than conventional thermal barrier coatings such as 7 weight% yttria stabilized zirconia.
  • a thermal barrier coating which exhibits such a lower thermal conductivity consists of at least 15 mol% of at least one lanthanide sesquioxide and the balance consists of ceria.
  • the ceria is present in an amount greater than 50 mol%.
  • Each lanthanide sesquioxide has a formula A 2 O 3 where A is selected from the group consisting of La, Pr, Nd, Sm, Eu, Tb, and mixtures thereof.
  • the at least one lanthanide sesquioxide is present in a total amount in the range of 15 to 45 mol%.
  • the at least one lanthanide sesquioxide is present in a total amount of at least 25 mol%.
  • Each cerium ion has more than one adjacent oxide vacancy on average, and preferably at least two adjacent oxide vacancies. The presence of these oxygen vacancies minimizes the thermal conductivity of the coating. Thus, they are a highly desirable feature of the coatings of the present invention.
  • the various thermal barrier coatings set forth herein may be characterized with a columnar structure.
  • the article has a substrate formed from ceramic material selected the group consisting of a monolithic ceramic material and a composite ceramic material.
  • a monolithic ceramic is meant to include, but is not limited to, single-phase or multi-phase ceramics, but not ceramics processed as composite (i.e. infiltrated fiber weaves, etc.).
  • monolithic ceramic substrates include, but are not limited to, silicon nitride and also self-reinforced silicon nitride.
  • composite ceramic substrates include, but are not limited to, SiC-SiC composites (vapor- or melt-infiltrated 2D or 3D fiber weaves) and C - C composites (again, vapor- or melt-infiltrated 2D or 3D fiber weavers).
  • the aforementioned thermal barrier coating is applied to the substrate.
  • the thermal barrier coating may be applied directly to a surface of the substrate or may be applied to a bond coat deposited on one or more surfaces of the substrate. Any suitable technique known in the art may be used to deposit a thermal barrier coating in accordance with one of the embodiments of the present invention. Suitable techniques include electron beam physical vapor deposition, chemical vapor deposition, LPPS techniques, and diffusion processes.
  • the bond coat may comprise any suitable bond coat known in the art.
  • the bond coat may be formed from an aluminium containing material, an aluminide, a platinum aluminide, a ceramic material, such as 7wt% yttria stabilized zirconia, or a MCrAlY material.
  • the bond coat may be multiple layers of ceramics which are designed to provide coefficient of thermal expansion match as well as to provide oxidation resistance (by blocking oxidation diffusion) and corrosion resistance (by blocking corrosive oxide liquid attack).
  • the multiple bond coat layers may be multiple distinct layers formed from the same or different materials. Additionally, the multiple bond coat layers may be functionally graded layers of mixtures of the above. In addition to serving as matching layers and bond coat layers, these layers act as environment barriers and oxygen barriers. Functional grading may be used to replace a distinct interface between two layers of dissimilar materials with a region in which the two materials are mixed such that the overall concentration gradually changes from 100% of the first material to 100% of the second material. Thus, a step change in concentration may be replaced with a gradually sloping change in concentration. This approach is effective in reducing residual stresses, for example between layers of materials with large thermal expansion mismatches.
  • the bond coat may be formed on the substrate, using any suitable process known in the art including, but not limited to, low pressure plasma spray, electron beam physical vapor deposition, diffusion processes and chemical vapor deposition processes. If desired, the bond coat may have an oxide scale on an outer surface, which oxide scale consists essentially of alumina.
  • the thermal barrier coatings of the present invention may be bonded to the oxide scale using any suitable technique known in the art.
  • a ceramic layer may be bonded to the thermal barrier coating.
  • the additional ceramic material may be selected from the group consisting of materials which reduce oxygen diffusion, provide erosion and abrasion resistance, and/or provide optical emissivity of 0.7.
  • high emissivity ceramic materials which can be used are alumina and mullite. High emissivity reduces the heat transfer across a thermal barrier coating by internal radiation (radiation of the thermal barrier coating material itself) due to the temperature difference between the hotter outer surface of the coating and the cooler interface between the coating and the TGO, thereby reducing the temperature of the TGO, thus the bondcoat, thus the ceramic.
  • high emissivity increases the insulative properties of the TBC.
  • the additional ceramic layer may be formed over an exterior surface of the thermal barrier coating.
  • the article may have an oxide scale on its surfaces and one of the thermal barrier coatings of the present invention may be applied directly over and bonded to the oxide scale using any suitable deposition technique known in the art including, but not limited to, diffusion processes, electron beam physical vapor deposition, and/or chemical vapor deposition techniques.
  • the oxide scale may consist substantially of alumina.
  • thermal barrier coatings of the present invention were developed for application in gas turbine engines, the coatings have utility in other applications where high temperatures are encountered, such as furnaces and internal combustion engines.

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Abstract

A turbine component has a substrate formed from a ceramic material selected from the group consisting of a monolithic ceramic material and a composite ceramic material and a thermal barrier coating bonded to the substrate. In one embodiment, the ceramic material forming the substrate is selected from the group of silicon nitride and self-reinforced silicon nitride. In another embodiment, the ceramic material forming the substrate is selected from the group consisting of a silicon carbide-silicon carbide material and a carbon-carbon material. At least one bond coat layer may be interposed between the substrate and the thermal barrier coating.

Description

  • The present invention relates to turbine components having a substrate formed from a ceramic material, such as a monolithic ceramic or a composite ceramic material, and a thermal barrier coating made from ceramic materials.
  • Gas turbine engines are well developed mechanisms for converting chemical potential energy, in the form of fuel, to thermal energy and then to mechanical energy for use in propelling aircraft, generating electrical power, pumping fluids, etc. At this time, the major available avenue for improved efficiency of gas turbine engines appears to be the use of higher operating temperatures. However, the metallic materials used in gas turbine engines are currently very near the upper limits of their thermal stability. In the hottest portion of modern gas turbine engines, metallic materials are used at gas temperatures above their melting points. They survive because they are air cooled. But providing air cooling reduces engine efficiency.
  • Accordingly, there has been extensive development of thermal barrier coatings for use with cooled gas turbine aircraft hardware. By using a thermal barrier coating, the amount of cooling air required can be substantially reduced, thus providing a corresponding increase in efficiency.
  • Such coatings are invariably based on ceramic. Mullite and alumina have been proposed, but zirconia is the current material of choice. Zirconia must be modified with a stabilizer to prevent the formation of the monoclinic phase. Typical stabilizers include yttria, calcia, ceria, and magnesia.
  • Zirconia based ceramics are resistant to water attack.
  • This is critical for land-based gas turbine applications, since the coatings are exposed at high temperatures for much longer than they are in aeroengine applications. Thus, corrosion of the thermal barrier coating can become a problem - indeed it is known to be a problem for silica-based thermal barrier coatings and alumina-based thermal barrier coatings. Steam is often injected into the combustor of land-based gas turbines to reduce nitric oxide formation, which exacerbates the water attack issue.
  • Hafnia and zirconate based materials for thermal/environmental barrier coating applications are disclosed in D. Zhu et al., NASA/TM-2003-212544.
  • Despite the success with thermal barrier coatings, there is a continuing desire for improved coatings which exhibit superior thermal insulation capabilities, especially those improved in insulation capabilities when normalized for coating density. Weight is always a critical factor when designing gas turbine engines, particularly rotating parts. Ceramic thermal barrier coatings are not load supporting materials, and consequently they add weight without increasing strength. There is a strong desire for a ceramic thermal barrier material which adds the minimum weight while providing the maximum thermal insulation capability. In addition, there are the normal desires for long life, stability and economy.
  • Accordingly, it is an object of the present invention to provide a turbine component having a ceramic material substrate and a thermal barrier coating having low thermal conductivity.
  • The foregoing object is attained by the turbine component of the present invention.
  • In accordance with the present invention, a turbine component is provided having a substrate formed from a ceramic material selected from the group consisting of a monolithic ceramic material and a composite ceramic material and a thermal barrier coating bonded to said substrate, said thermal barrier coating consisting of at least 15 mol% of at least one lanthanide sesquioxide and the balance consisting of ceria.
  • The ceria is preferably present in an amount greater than 50 mol%. The at least one lanthanide sesquioxide preferably has a formula A2O3 where A is selected from the group consisting of La, Pr, Nd, Sm, Eu, Tb, and mixtures thereof.
  • Certain preferred embodiments of the present invention will now be explained in greater detail by way of example only.
  • The essence of the present invention arises from the discovery that certain ceramic materials have great utility as thermal barrier coatings on ceramic material substrates, particularly those used to form components, such as the airfoils, of turbine engine components. These ceramic coating materials have such utility because they exhibit lower thermal conductivity than conventional thermal barrier coatings such as 7 weight% yttria stabilized zirconia.
  • In accordance with the present invention, a thermal barrier coating which exhibits such a lower thermal conductivity consists of at least 15 mol% of at least one lanthanide sesquioxide and the balance consists of ceria. Preferably, the ceria is present in an amount greater than 50 mol%. Each lanthanide sesquioxide has a formula A2O3 where A is selected from the group consisting of La, Pr, Nd, Sm, Eu, Tb, and mixtures thereof. In a preferred embodiment, the at least one lanthanide sesquioxide is present in a total amount in the range of 15 to 45 mol%. In a most preferred embodiment, the at least one lanthanide sesquioxide is present in a total amount of at least 25 mol%. Each cerium ion has more than one adjacent oxide vacancy on average, and preferably at least two adjacent oxide vacancies. The presence of these oxygen vacancies minimizes the thermal conductivity of the coating. Thus, they are a highly desirable feature of the coatings of the present invention.
  • The various thermal barrier coatings set forth herein may be characterized with a columnar structure.
  • An article, having particular utility as a component in a gas turbine engine, is provided in accordance with the present invention. The article has a substrate formed from ceramic material selected the group consisting of a monolithic ceramic material and a composite ceramic material. As used herein, the term "monolithic ceramic" is meant to include, but is not limited to, single-phase or multi-phase ceramics, but not ceramics processed as composite (i.e. infiltrated fiber weaves, etc.). Examples of monolithic ceramic substrates include, but are not limited to, silicon nitride and also self-reinforced silicon nitride. Examples of composite ceramic substrates include, but are not limited to, SiC-SiC composites (vapor- or melt-infiltrated 2D or 3D fiber weaves) and C - C composites (again, vapor- or melt-infiltrated 2D or 3D fiber weavers).
  • The aforementioned thermal barrier coating is applied to the substrate. The thermal barrier coating may be applied directly to a surface of the substrate or may be applied to a bond coat deposited on one or more surfaces of the substrate. Any suitable technique known in the art may be used to deposit a thermal barrier coating in accordance with one of the embodiments of the present invention. Suitable techniques include electron beam physical vapor deposition, chemical vapor deposition, LPPS techniques, and diffusion processes.
  • When a bond coat is used, the bond coat may comprise any suitable bond coat known in the art. For example, the bond coat may be formed from an aluminium containing material, an aluminide, a platinum aluminide, a ceramic material, such as 7wt% yttria stabilized zirconia, or a MCrAlY material. Alternatively, the bond coat may be multiple layers of ceramics which are designed to provide coefficient of thermal expansion match as well as to provide oxidation resistance (by blocking oxidation diffusion) and corrosion resistance (by blocking corrosive oxide liquid attack). Suitable bond coats may be formed from Ta2O5, all rare-earth disilicates having the formula X2Si207 where X = La, Nd, Pr, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, Lu, and mixtures thereof, Y2Si2O7, mullite, BSAS (barium strontium alumino silicate or celsian), yttrium aluminum garnet, ytterbium aluminum garnet, and other rare-earth aluminate garents where the rare earth element is selected from the group consisting of Gd, Tb, Dy, Ho, Er, Tm, Lu, and mixtures thereof. The multiple bond coat layers may be multiple distinct layers formed from the same or different materials. Additionally, the multiple bond coat layers may be functionally graded layers of mixtures of the above. In addition to serving as matching layers and bond coat layers, these layers act as environment barriers and oxygen barriers. Functional grading may be used to replace a distinct interface between two layers of dissimilar materials with a region in which the two materials are mixed such that the overall concentration gradually changes from 100% of the first material to 100% of the second material. Thus, a step change in concentration may be replaced with a gradually sloping change in concentration. This approach is effective in reducing residual stresses, for example between layers of materials with large thermal expansion mismatches.
  • The bond coat may be formed on the substrate, using any suitable process known in the art including, but not limited to, low pressure plasma spray, electron beam physical vapor deposition, diffusion processes and chemical vapor deposition processes. If desired, the bond coat may have an oxide scale on an outer surface, which oxide scale consists essentially of alumina. The thermal barrier coatings of the present invention may be bonded to the oxide scale using any suitable technique known in the art.
  • If desired, a ceramic layer may be bonded to the thermal barrier coating. The additional ceramic material may be selected from the group consisting of materials which reduce oxygen diffusion, provide erosion and abrasion resistance, and/or provide optical emissivity of 0.7. Examples of high emissivity ceramic materials which can be used are alumina and mullite. High emissivity reduces the heat transfer across a thermal barrier coating by internal radiation (radiation of the thermal barrier coating material itself) due to the temperature difference between the hotter outer surface of the coating and the cooler interface between the coating and the TGO, thereby reducing the temperature of the TGO, thus the bondcoat, thus the ceramic. Thus, high emissivity increases the insulative properties of the TBC. The additional ceramic layer may be formed over an exterior surface of the thermal barrier coating.
  • In some embodiments, the article may have an oxide scale on its surfaces and one of the thermal barrier coatings of the present invention may be applied directly over and bonded to the oxide scale using any suitable deposition technique known in the art including, but not limited to, diffusion processes, electron beam physical vapor deposition, and/or chemical vapor deposition techniques. The oxide scale may consist substantially of alumina.
  • Although the thermal barrier coatings of the present invention were developed for application in gas turbine engines, the coatings have utility in other applications where high temperatures are encountered, such as furnaces and internal combustion engines.

Claims (17)

  1. A turbine component having a substrate formed from a ceramic material selected from the group consisting of a monolithic ceramic material and a composite ceramic material and a thermal barrier coating bonded to said substrate, said thermal barrier coating consisting of at least 15 mol% of at least one lanthanide sesquioxide and the balance consisting of ceria.
  2. A turbine component according to claim 1, wherein the ceria is present in an amount greater than 50 mol%.
  3. A turbine component according to claim 2, wherein the at least one lanthanide sesquioxide has a formula A2O3 where A is selected from the group consisting of La, Pr, Nd, Sm, Eu, Tb, and mixtures thereof.
  4. A turbine component according to claim 2 or 3, wherein said at least one lanthanide sesquioxide is present in a total amount in the range of 15 to 45 mol%.
  5. A turbine component according to claim 4, wherein said at least one lanthanide sesquioxide is present in a total amount of at least 25 mol%
  6. A turbine component according to claim 1, wherein said ceramic material is selected from the group of silicon nitride and self-reinforced silicon nitride.
  7. A turbine component according to claim 1, wherein said ceramic material is selected from the group consisting of a silicon carbide-silicon carbide material and a carbon-carbon material.
  8. A turbine component according to any preceding claim, further comprising at least one bond coat layer between said substrate and said thermal barrier coating, and said at least one bond coat layer providing coefficient of thermal expansion matching, oxidation resistance and corrosion resistance.
  9. A turbine component according to claim 8, wherein said at least one bond coat layer is formed from Ta2O5.
  10. A turbine component according to claim 8, wherein said at least one bond coat layer is formed from a rare-earth disilicate having the formula X2Si207 where X is selected from the group consisting of La, Nd, Pr, Sm, Eu, Gd, Tb, Dy, Ho, Er, Tm, Yb, and Lu.
  11. A turbine component according to claim 8, wherein said at least one bond coat layer comprises Y2Si2O7.
  12. A turbine component according to claim 8, wherein said at least one bond coat layer comprises mullite.
  13. A turbine component according to claim 8, wherein said at least one bond coat layer comprises barium strontium alumino silicate.
  14. A turbine component according to claim 8, wherein said at least one bond coat layer comprises yttrium aluminum garnet.
  15. A turbine component according to claim 8, wherein said at least one bond coat layer comprises ytterbium aluminium garnet.
  16. A turbine component according to claim 8, wherein said at least one bond coat layer comprises rare-earth aluminate garnets wherein the rare earth is selected from the group consisting of Gd, Tb, Dy, Ho, Er, Tm, Lu, and mixtures thereof.
  17. A turbine component according to claim 8, wherein said bond coat is formed from a plurality of functionally graded layers.
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MXPA05002921A (en) 2005-09-21
PL373690A1 (en) 2005-09-19
US7226672B2 (en) 2007-06-05
EP1577499A3 (en) 2006-12-27
CA2500753A1 (en) 2005-09-17
SG115766A1 (en) 2005-10-28
US20040175597A1 (en) 2004-09-09
JP2005263625A (en) 2005-09-29
ATE434714T1 (en) 2009-07-15
RU2005107462A (en) 2006-08-27
KR100736296B1 (en) 2007-07-06
KR20060043438A (en) 2006-05-15
CN1670337A (en) 2005-09-21
DE602005015049D1 (en) 2009-08-06
EP1577499A2 (en) 2005-09-21

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